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首页> 外文期刊>International Journal of Heat and Mass Transfer >Inverse Estimation Of Heat Flux And Temperature On Nozzlernthroat-insert Inner Contour
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Inverse Estimation Of Heat Flux And Temperature On Nozzlernthroat-insert Inner Contour

机译：喷嘴喉部内轮廓的热通量和温度的逆估计

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摘要

During the missile flight, the jet flow with high temperature comes from the heat flux of propellant burning. An enormous heat flux from the nozzle throat-insert inner contour conducted into the nozzle shell will degrade the material strength of nozzle shell and reduce the nozzle thrust efficiency. In this paper, an on-line inverse method based on the input estimation method combined with the finite-element scheme is proposed to inversely estimate the unknown heat flux on the nozzle throat-insert inner contour and the inner wall temperature by applying the temperature measurements of the nozzle throat-insert. The finite-element scheme can easily define the irregularly shaped boundary. The superior capability of the proposed method is demonstrated in two major time-varying estimation cases. The computational results show that the proposed method has good estimation performance and highly facilitates the practical implementation. An effective analytical method can be offered to increase the operation reliability and thermal-resistance layer design in the solid rocket motor.
机译：在导弹飞行期间，高温喷射流来自推进剂燃烧的热通量。来自喷嘴喉部插入内部轮廓的巨大热通量传导到喷嘴壳中，会降低喷嘴壳的材料强度并降低喷嘴推力效率。本文提出了一种基于输入估计方法与有限元方案相结合的在线逆方法，通过应用温度测量值逆估计喷嘴喉道内轮廓和内壁温度上的未知热通量。喷嘴喉部插入的有限元方案可以轻松定义不规则形状的边界。在两种主要的时变估计情况下证明了该方法的优越性能。计算结果表明，该方法具有良好的估计性能，极大地促进了实际实现。可以提供一种有效的分析方法来提高固体火箭发动机的运行可靠性和热阻层设计。

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